AG36 (ag36-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AG36 (ag36-il) Reynolds number: 500,000 Max Cl/Cd: 81.02 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag36-il-500000-n5.txt Download as CSV file: xf-ag36-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG36
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5459 0.08727 0.08505 -0.0058 1.0000 0.0082
-10.000 -0.5493 0.08189 0.07970 -0.0094 1.0000 0.0082
-9.750 -0.5545 0.07615 0.07400 -0.0142 1.0000 0.0082
-9.500 -0.5551 0.06809 0.06593 -0.0237 1.0000 0.0082
-9.250 -0.5549 0.05722 0.05496 -0.0346 1.0000 0.0083
-9.000 -0.5968 0.02470 0.02065 -0.0457 1.0000 0.0086
-8.750 -0.5790 0.02165 0.01709 -0.0449 1.0000 0.0088
-8.500 -0.5595 0.01946 0.01453 -0.0441 1.0000 0.0092
-8.250 -0.5373 0.01856 0.01353 -0.0433 1.0000 0.0095
-8.000 -0.5146 0.01780 0.01266 -0.0425 1.0000 0.0099
-7.750 -0.4871 0.01681 0.01150 -0.0427 0.9982 0.0103
-7.500 -0.4545 0.01561 0.01008 -0.0439 0.9949 0.0107
-7.250 -0.4225 0.01457 0.00884 -0.0449 0.9906 0.0112
-7.000 -0.3904 0.01369 0.00780 -0.0458 0.9857 0.0118
-6.750 -0.3585 0.01298 0.00697 -0.0467 0.9802 0.0122
-6.500 -0.3275 0.01213 0.00600 -0.0474 0.9735 0.0128
-6.250 -0.2963 0.01161 0.00545 -0.0481 0.9663 0.0136
-6.000 -0.2652 0.01125 0.00505 -0.0487 0.9573 0.0148
-5.750 -0.2357 0.01085 0.00459 -0.0489 0.9464 0.0159
-5.500 -0.2069 0.01048 0.00413 -0.0489 0.9330 0.0167
-5.250 -0.1796 0.00999 0.00358 -0.0487 0.9171 0.0182
-5.000 -0.1528 0.00972 0.00325 -0.0482 0.8971 0.0198
-4.750 -0.1266 0.00952 0.00293 -0.0475 0.8716 0.0218
-4.500 -0.1003 0.00929 0.00262 -0.0469 0.8512 0.0252
-4.250 -0.0735 0.00914 0.00238 -0.0465 0.8322 0.0290
-4.000 -0.0464 0.00898 0.00215 -0.0461 0.8152 0.0350
-3.750 -0.0193 0.00883 0.00196 -0.0459 0.7979 0.0466
-3.500 0.0080 0.00869 0.00180 -0.0456 0.7788 0.0650
-3.250 0.0352 0.00850 0.00166 -0.0454 0.7587 0.0982
-2.750 0.0895 0.00806 0.00143 -0.0452 0.7155 0.2121
-2.500 0.1164 0.00784 0.00136 -0.0451 0.6825 0.2920
-2.250 0.1426 0.00768 0.00128 -0.0448 0.6319 0.3790
-2.000 0.1689 0.00745 0.00124 -0.0447 0.6039 0.4881
-1.750 0.1946 0.00708 0.00125 -0.0444 0.5852 0.6344
-1.500 0.2179 0.00666 0.00129 -0.0433 0.5709 0.7901
-1.250 0.2392 0.00641 0.00134 -0.0412 0.5589 0.9231
-1.000 0.2805 0.00644 0.00132 -0.0440 0.5460 0.9907
-0.750 0.3115 0.00654 0.00132 -0.0446 0.5348 1.0000
-0.500 0.3388 0.00663 0.00134 -0.0445 0.5239 1.0000
-0.250 0.3663 0.00672 0.00137 -0.0444 0.5131 1.0000
0.000 0.3938 0.00682 0.00140 -0.0443 0.5022 1.0000
0.250 0.4213 0.00693 0.00144 -0.0442 0.4905 1.0000
0.500 0.4488 0.00704 0.00149 -0.0442 0.4781 1.0000
0.750 0.4765 0.00714 0.00154 -0.0442 0.4640 1.0000
1.000 0.5041 0.00725 0.00160 -0.0441 0.4477 1.0000
1.250 0.5315 0.00739 0.00167 -0.0441 0.4292 1.0000
1.500 0.5588 0.00755 0.00176 -0.0441 0.4091 1.0000
1.750 0.5861 0.00773 0.00186 -0.0440 0.3881 1.0000
2.000 0.6131 0.00795 0.00198 -0.0440 0.3648 1.0000
2.250 0.6401 0.00817 0.00212 -0.0439 0.3414 1.0000
2.500 0.6670 0.00842 0.00229 -0.0439 0.3200 1.0000
2.750 0.6939 0.00866 0.00246 -0.0439 0.2978 1.0000
3.000 0.7207 0.00894 0.00266 -0.0438 0.2757 1.0000
3.250 0.7472 0.00924 0.00288 -0.0438 0.2513 1.0000
3.500 0.7737 0.00955 0.00311 -0.0437 0.2269 1.0000
3.750 0.8000 0.00988 0.00336 -0.0437 0.2048 1.0000
4.000 0.8262 0.01024 0.00363 -0.0436 0.1817 1.0000
4.250 0.8520 0.01064 0.00394 -0.0435 0.1569 1.0000
4.500 0.8776 0.01108 0.00428 -0.0434 0.1322 1.0000
5.000 0.9286 0.01194 0.00498 -0.0431 0.0938 1.0000
5.250 0.9536 0.01242 0.00540 -0.0430 0.0752 1.0000
5.500 0.9784 0.01293 0.00583 -0.0428 0.0582 1.0000
5.750 1.0028 0.01348 0.00632 -0.0425 0.0427 1.0000
6.000 1.0268 0.01407 0.00685 -0.0423 0.0305 1.0000
6.250 1.0509 0.01465 0.00741 -0.0420 0.0223 1.0000
6.500 1.0749 0.01521 0.00799 -0.0416 0.0175 1.0000
6.750 1.0989 0.01575 0.00858 -0.0413 0.0147 1.0000
7.000 1.1219 0.01642 0.00928 -0.0409 0.0123 1.0000
7.250 1.1454 0.01698 0.00992 -0.0405 0.0108 1.0000
7.500 1.1682 0.01761 0.01061 -0.0401 0.0095 1.0000
7.750 1.1898 0.01839 0.01146 -0.0395 0.0085 1.0000
8.000 1.2118 0.01907 0.01224 -0.0389 0.0079 1.0000
8.250 1.2331 0.01982 0.01308 -0.0383 0.0073 1.0000
8.500 1.2536 0.02061 0.01396 -0.0377 0.0068 1.0000
8.750 1.2729 0.02151 0.01494 -0.0369 0.0064 1.0000
9.000 1.2890 0.02272 0.01628 -0.0357 0.0060 1.0000
9.250 1.3060 0.02375 0.01743 -0.0346 0.0058 1.0000
9.500 1.3220 0.02481 0.01862 -0.0335 0.0057 1.0000
9.750 1.3363 0.02598 0.01992 -0.0322 0.0055 1.0000
10.000 1.3486 0.02724 0.02131 -0.0306 0.0053 1.0000
10.250 1.3586 0.02858 0.02279 -0.0289 0.0051 1.0000
10.500 1.3637 0.02997 0.02432 -0.0265 0.0050 1.0000
10.750 1.3672 0.03154 0.02603 -0.0243 0.0049 1.0000
11.000 1.3693 0.03334 0.02798 -0.0225 0.0048 1.0000
11.250 1.3706 0.03538 0.03016 -0.0211 0.0047 1.0000
11.500 1.3711 0.03771 0.03263 -0.0203 0.0046 1.0000
11.750 1.3703 0.04041 0.03548 -0.0201 0.0045 1.0000
12.000 1.3682 0.04352 0.03873 -0.0204 0.0044 1.0000
12.250 1.3647 0.04709 0.04244 -0.0213 0.0044 1.0000
12.500 1.3590 0.05125 0.04676 -0.0228 0.0043 1.0000
12.750 1.3514 0.05605 0.05171 -0.0250 0.0043 1.0000
13.000 1.3415 0.06135 0.05717 -0.0274 0.0042 1.0000
13.250 1.3292 0.06712 0.06309 -0.0301 0.0042 1.0000
13.500 1.3149 0.07329 0.06941 -0.0329 0.0042 1.0000
13.750 1.2989 0.07989 0.07616 -0.0360 0.0042 1.0000
14.000 1.2821 0.08681 0.08322 -0.0392 0.0042 1.0000
14.250 1.2648 0.09407 0.09062 -0.0427 0.0042 1.0000
14.500 1.2466 0.10176 0.09844 -0.0463 0.0042 1.0000
14.750 1.2289 0.10956 0.10637 -0.0501 0.0042 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG36 (ag36-il)